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Aircraft attitude non-singular predetermined time sliding mode control method

A technology of predetermined time and control method, applied in the direction of attitude control, etc., can solve the problems that cannot meet the requirements of aircraft control performance, and achieve the effect of ensuring rationality, avoiding strange phenomena, and avoiding excessive overshoot

Active Publication Date: 2022-07-15
哈尔滨逐宇航天科技有限责任公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The characteristics of fast time-varying, strong coupling, strong nonlinearity, and large uncertainty in the flight process of the aircraft make traditional control methods unable to meet the needs of the aircraft for control performance.

Method used

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  • Aircraft attitude non-singular predetermined time sliding mode control method
  • Aircraft attitude non-singular predetermined time sliding mode control method
  • Aircraft attitude non-singular predetermined time sliding mode control method

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Embodiment Construction

[0012] The technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments, based on the present invention The embodiments in the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work, fall within the protection scope of the present invention.

[0013] A non-singular predetermined time sliding mode control method for aircraft attitude, the method comprising the following steps:

[0014] S1: Establish the attitude dynamics and kinematics model of the aircraft reentry process, and obtain the attitude tracking error state equation after making the difference between the attitude variable and the guidance command;

[0015] S101: The equations for establishing the attitude dynamics an...

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Abstract

The invention discloses an aircraft attitude non-singular predetermined time sliding mode control method, and belongs to the technical field of aircraft attitude control. The method comprises the following steps: obtaining an attitude tracking error state equation; using error conversion to convert inequality constraints into equality constraints, and establishing an error conversion model; enabling the state error to converge to zero within a predefined convergence time when the state error runs to the sliding mode surface; a non-singular sliding mode control law with a preset time convergence characteristic is established, and system state errors are converged to a sliding mode surface within preset time on the premise of avoiding singularity. According to the method, the predetermined time nonsingular sliding mode controller is adopted, it is guaranteed that attitude tracking errors in the dynamic process or the steady process in the aircraft attitude tracking process are limited within a predefined boundary range, overshoot in the dynamic process is avoided, the controller can achieve convergence within any predetermined time, and the attitude tracking precision is improved. Meanwhile, the singularity phenomenon is avoided, and the reasonability of the control instruction is ensured.

Description

technical field [0001] The invention relates to a non-singular predetermined time sliding mode control method for aircraft attitude, which belongs to the technical field of aircraft attitude control. Background technique [0002] In order to increase the maneuvering range of the aircraft, the complex slender body configuration with high lift-to-drag ratio is often used, which leads to its significant time-varying characteristics under complex effects such as aerodynamic / thermal / structural coupling. Its wide speed range and wide airspace flight characteristics lead to the characteristics of large certainty in the variation range of model parameters. The rapid time-varying, strong coupling, strong nonlinearity, and large uncertainty in the flight process of aircraft make traditional control methods unable to meet the control performance requirements of aircraft. Therefore, seeking a nonlinear time-varying, strong robust advanced flight control method with fast response speed ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833
Inventor 韦常柱浦甲伦朱光楠张峪浩王铭泽
Owner 哈尔滨逐宇航天科技有限责任公司
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